Gas-actuated emergency pilot release system

ABSTRACT

A gas-actuated release system is incorporated into a conventional ejection seat of an aircraft for freeing a pilot from his survival gear which could hinder his escape from the aircraft in a ground emergency. The system includes fail-safe features which prevent its operation when the pilot ejects from the aircraft via the ejection seat system. Flexible gas lines between the survival gear and the ejection seat are equipped with tension release connectors which pull apart upon separation of the pilot and survival gear from the ejection seat after ejection from the aircraft.

United States Patent [191 Poehlmann GAS-ACTUATED EMERGENCY PILOT RELEASESYSTEM [75] Inventor: Paul W. Poehlmann, Stinson Beach,

Calif.

[73] Assignee: H. Koch and Sons, Inc.

[22] Filed: Nov. 19, 1973 [21] Appl. No.: 417,140

[52] US. Cl. 244/122 A; 24/73 PH; 24/205.l7; 24/230 AN; 244/141; 244/151A [51] Int. Cl 864d 25/06; 864d 25/10 [58] Field 01Search..... 244/122A, 122 R, 122 AH, 244/122 AG, 141, 151 R, 151 A, 151 B;

24/73 PH, 205.17, DIG. 26, 230 AN, 230

NP, 230 AL, 230 AV; 297/385; 403/15 [56] References Cited UN1TED STATESPATENTS Gaylord 244/151 A X [451 May 20, 1975 10/1973 Gaylord 244/151 A1/1974 Gaylord 244/151 A Primary Examiner-Trygve M. Blix AssistantExaminer-Barry L. Kelmachter Attorney, Agent. or Firm-George B. WhiteABSTRACT A gasactuated release system is incorporated into aconventional ejection seat of an aircraft for freeing a pilot from hissurvival gear which could hinder his escape from the aircraft in aground emergency. The system includes fail-safe features which preventits operation when the pilot ejects from the aircraft via the ejectionseat system. Flexible gas lines between the survival gear and theejection seat are equipped with tension release connectors which pullapart upon separation of the pilot and survival gear from the ejectionseat after ejection from the aircraft.

18 Claims, 23 Drawing Figures PATENTEI] HAYZO I975 SHEU Pmzmmm w s3,884,436

SHEET 5 OF 9 FIG. 5b

PATENTEB HAYZOISYS 3 4 43 SHEET E OF 9 PATENTED MAY 2 0 I975 SHEET 70F 9FIG. 6d

PATENTED HAY 2 0 I575 SHEET 8 BF GAS-ACTUATED EMERGENCY PILOT RELEASESYSTEM FIELD OF THE INVENTION The invention relates to a cold gaspressure system incorporated into a conventional ejection seat systemfor freeing an aircraft pilot from his survival kit and parachute canopyhindering his escape from an aircraft in a ground emergency. Particularnovel features of the invented system include cold gas driven releasablelatches and tension release gas line connectors. Other features of theinvented system relate to a fail-safe actuator which separates the gassource from the remaining release system when the pilot utilizes theejection seat to escape from his aircraft.

DESCRIPTION OF THE PRIOR ART Sophisticated aircraft are equipped withejection seat systems which enable a pilot to escape from the aircraft.In a typical ejection seat system, a parachute canopy package is securedto the scat behind the pilot. A survival kit is usually disposed in theseat of the system upon which the pilot sits. The pilot enters thecockpit of his aircraft wearing a parachute harness which he connects tothe riser straps of the packed parachute and to straps of the survivalkit. The pilot then secures himself in the seat with a shoulder harness,a lap belt and leg or garter straps.

Upon a ground emergency it is essential that the pilot be able to escapefrom the aircraft as quickly as possible. Accordingly, typical ejectionseat systems are equipped with emergency ground egress releasemechanisms which free the pilot from the shoulder harness, lap belt andleg restraint straps upon pulling a single lever. However, the pilotmust execute separate maneuvers to separate himself from the parachutecanopy and from the survival kit. Such separate maneuvers aredeliberately required so as to prevent the pilot from inadvertentlyreleasing himself from the parachute and survival kit when he ejectsfrom the aircraft.

However, in an emergency situation on the ground with existing ejectionseat systems, the pilot, after freeing himself from the ejection seat,must either attempt egress from the aircraft with his parachute andsurvival kit or free himself from the parachute and survival kit andthen attempt egress from the aircraft.

Various release systems exist which expedite a pilots egress fromaircraft on the ground. For example, a gasactuated release system isdescribed in U.S. Pat. No. 3,658,28l issued to Mr. John. A. Gaylord inwhich a pilot releases himself from his parachute harness by puncturinga high pressure gas canister mounted on the harness which thensimultaneously disconnects all the strap connectors holding the harnesstogether. The gas canister is punctured by a single manual maneuver.Another approach is exemplified by the single point parachute harnessrelease mechanism described in U.S. Pat. No. 3,692,262 also issued toMr. John A. Gaylord wherein all the straps of the harness are secured bya single releasable locking mechanism located at the pilot's waist.

Summarizing, existing strap release systems in ejection seats require apilot to manually operate a minimum of two or three release mechanismsto free himself from the seat and encumbrances hindering his egress fromthe aircraft on the ground. In emergency ground situations where thepilot is dazed, injured or simply confused and forgetful, the time delayrequired for executing two or more manual maneuvers in order to escapefrom the aircraft can prove fatal.

In addition, if a pilot utilizes a typical ejection seat system toescape from his aircraft, he must be automatically separated from thatsystem together with his parachute and survival kit after a short delay.Accordingly, the number of mechanical connections between the ejectionseat system and the pilot, parachute or survival kit are kept to anabsolute minimum because of the possibility of failure ofone of theconnections to release, thus tying the massive ejection seat system tothe pilot after ejection. In such instances, the pilot would fall to hisdeath inasmuch as his parachute could not support both him and theejection seat safely.

SUMMARY OF THE INVENTION A gas-actuated release system is incorporatedinto a conventional ejection seat system of an aircraft for releasing apilot from straps connecting him to his parachute and survival kit. Therelease system is energized by the pilot manually operating an existingemergency ground egress release mechanism which also frees him fromother devices restraining him in the ejection seat. Thus, by a singlemanual maneuver, a pilot can free himself from all straps andencumbrances which would hinder or slow his escape from the aircraft incase of a ground emergency.

The described gas-actuated release system includes a positive interlockmechanism which frees and ejects the gas source from the system when thepilot energizes the ejection seat mechanism for escape from theaircraft. Thus, the pilot is positively prevented from inadvertentlyfreeing himself from his parachute and survival gear when he utilizesthe ejection seat to escape from the aircraft.

Latching devices of the invented release system secure the parachute andthe survival package to the parachute harness worn by the pilot anddisengage responsive to gas pressure. Gas pressure is supplied by acartridge mounted in a piercing mechanism on the body of the ejectionseat. The latching devices are connected to the ejection seat byflexible high pressure conduits equipped with tension releaseconnectors.

In particular, the tension release connectors of the inventedgas-actuated release system are designed to pull apart absent gaspressurization. Thus, the described connectors enable the ejection seatto fall free of, or separate from, the pilot, together with hisparachute and survival kit after ejection from the aircraft. Theconnectors also include means for positive locking action upon gaspressurization thus preventing inadvertant depressurization of the gasrelease system when it is activated.

DESCRIPTION OF THE FIGURES FIG. 1 is a partially cutaway perspectiveview of a Martin-Baker ejection seat system, showing the location of thegas-actuated latches, the flexible gas lines and the tension release gasline connectors.

FIGS. 2 and 20 show a rear view of the ejection seat showing thelocation of the gas lines and the piercingdecoupling interlock device ofthe gas-actuated release system.

FIG. 3 is a perspective view of the connection be tween the decouplinginterlock system and the ejection release system of the ejection seat.

FIGS. 40 through f show the details of the canister piercing-decouplinginterlock mechanism of the gasactuated release system.

FIGS. 50 through f show the details of the gasenergized releasable latchfor securing the survival kit to the parachute harness of the pilot.

FIGS. 60 through f show the details of the gasenergized releasablelatching mechanisms between the parachute pack and the parachuteharness.

FIGS. 70, b, c & d show the details of the tension release gas lineconnectors.

DETAILED DESCRIPTION OF THE INVENTION Referring to FIG. I, theconventional ejection seat system II is shown. A parachute pack 12 ismounted on the back of the ejection seat ll above the back cushion l3behind the head of the pilot if he were sitting in the seat 11. Asurvival pack 14 is disposed in the seat of the system 11. Gas-energizedreleasable latches 16 are secured to riser straps 17 to the parachutepack 12. Gas-energized releasable latches 18 mounted on the survivalpackage 14 secure straps 19 which are adapted to be connected to aparachute harness worn by a pilot. Flexible gas lines 21 connect betweenthe latches l6 & l8 and gas source mounted on the back of the seatsystem I]. Tension release gas line connectors 22 are incorporated intothe flexible gas lines 21.

To eject from the aircraft, the pilot pulls either the face curtainejection bails 23 above his head or the seat ejection ball 24 located inthe center of the seat between his legs. To release himself from allstraps connecting him to the ejection seat system II, the parachute pack12 and the survival pack 14, the pilot pulls the emergency ground egressrelease handle 26 upwards. As shown in FIG. I, the strap release lever26 is located on the right arm of the ejection seat system ll proximatethe pilot's right hand if he were sitting in the system.

DETAILED DESCRIPTION OF THE CANISTER PlERClNG-DECOUPLING DEVICEReferring now to FIGS. 2 and showing the rear perspective view of theejection seat 11 and the canister piercing-decoupling interlock device27, the piercing mechanism 28 of the device 27 is operated by amechanical linkage (not shown) including a rocking shaft 29 operativelyconnected to the release lever 26 by conventional mechanical means. Inparticular, pulling the release lever up causes the lever 31 on the sidestructure of the ejection seat system 11 to rotate clockwise pushing abar 32 into the piercing mechanism 28 of the interlock device 27 topierce the membrane of the canister 33 containing a high pressure gas.The details of the piercing mechanism are described below.

After the canister 33 is pierced, high pressure gas flows into rigid gaslines mounted on the structure of the ejection seat system to theflexible gas lines 21. As shown in FIG. 2, the flexible gas lines 21 aredisconnected from the lines going to the releasable latches at thetension release gas line connectors 22.

The interlock mechanism of the device 27 comprises a retainer clip 34which is adapted to be pulled free of the device 27 whereupon a springejects the gas canister 33 from the device 27 (described below ingreater detail). A cable 36 is connected between the retainer clip 34and a pulley 37 rigidly mounted on a shaft 38.

In more detail, referring to FIG. 3, the cable 36 is secured byconventional means to the pulley 37 which is rigidly mounted on theshaft 38. The shaft 38 rotates counterclockwise when the pilot pullseither the face curtain ejection bail 23 or the seat ejection bail 24.Accordingly, when the face curtain or seat ejection bails, 23 and 24respectively, are pulled, the cable 36 pulls the retainer clip 34 out ofthe interlock mechanism of the device 27 and the gas canister 33 isejected therefrom. Thus it is impossible for the pilot to inadvertentlyenergize the gas-actuated release system when he ejects from hisaircraft in the air. However, if the ejection seat system 11 fails tooperate after the pilot has pulled the ejection bails 23 & 24, the pilotcan still pull the emer gency ground egress release handle 26 to freehimself from straps confining him to the ejection seat system I1 withoutfreeing himself from his parachute, and sur vival kit, thus leaving himfree to attempt to escape from his aircraft by other maneuvers.

Referring now to FIGS. 4a, b, & c, the canister piercing-decouplinginterlock device 27 comprises a housing having a rectangular slot 41 forreceiving the bar 32 and a hollow cylindrical housing 42 perpendicularlydisposed with respect to the slot 41 for receiving a gas canister pack.A canister piercing plunger 44 is received in a cylindrical port 46communicating between the slot 41 and the cylindrical housing 42. Thecylindrical port 46 is coaxially aligned with the cylindrical housing42. The canister piercing plunger includes an annular slot for receivingan O-ring for making a hermetic seal between the plunger 44 and thewalls of the cylindrical port 46. The O-ring 47 also serves to hold theplunger 44 in a non-piercing position (see FIG. 4b).

Referring to FIGS. 4!) and c, the head of the plunger 44 is rounded andprojects outward from the cylindrical port 46 into the slot 41. The bar32 has a recess 48 for receiving the rounded head of the plunger 44 (seeFIG. 4c). The shoulder 49 of the recess is perpendicular with respect tothe axis of the bar 32 to prevent the bar from sliding longitudinallyinto slot 41 in a direction indicated by the arrow 70. The othershoulder SI of the recess 48 is inclined with respect to the axis of thebar 32 such that when the bar is pushed in a direction indicated by thearrow 52 by the mechanical linkage 29 (see FIG. 2), the plunger 44 isdriven into the cylindrical port 46 and pierces the gas canister 33. Theend of the bar 32 is also cutaway beyond the inclined shoulder 51 whichallows gas pressure to force the plunger 44 back out into the slot 41.

Referring now to FIG. 4a, the gas canister pack 43 includes acylindrical cup 53 with a port 54 drilled coaxially through its bottom.The port 54 is threaded for receiving a conventional high pressure gascanister 33. A conventional seal 56 is disposed between a shoulderwithin the port and the neck of the canister 33. The cylindrical cup 53includes an annular slot 57 around its outside surface proximate to theclosed end for receiving an O-ring seal 58 and an annular shoulder 59 atits open end of a slightly greater diameter than its outer diameter.

The gas canister pack is adapted to be inserted into the hollow housing42. The O-ring seal 58 makes a hermetic seal between the inner walls ofthe housing 42 and the outer walls of the cup 53. The inner wall of thehollow cylindrical housing 42 is relieved proximate its open end to adiameter slightly greater than that of the annular shoulder 57 toprovide an annular shoulder 61 within the hollow housing 42. A spring 60is compressed between the annular shoulder 59 at the open end of the cup53 and the annular shoulder 6] within the housing 42.

Referring to FIGS. 4d 8: 4e, two slots 62 are cut through the wall ofthe open end for receiving the prongs 63 of the retainer clip 34 (seeFlG. 4c). The ends of the prongs 63 of the retainer clip 34 are adaptedto clip onto a ring 65 mounted around the gas canister 33 with a slightcompressive force such that the clip will not vibrate out of the slot62. As shown in FIG. 4d, the annular shoulder 59 of the gas canisterpack 43 engages the inner edge of the prongs 63 and the outer edge ofthe prongs 63 engage the wall of the cylindrical housing 42. Thus. theretainer clip 34 se cures the gas canister pack 43 within the hollowcylindrical housing 42 of the canister piercing-decoupling interlockdevice 27.

The piercing mechanism of the device 27 operates in the followingfashion: the pilot pulls the strap release lever 26 causing themechanical linkage 29 to drive the bar 32 in a direction indicated bythe arrow 52. The inclined shoulder 51 of the bar drives the canisterpiercing plunger 44 into the cylindrical port 46 piercing the diaphramon the gas canister bottle 33. The gas pressure in the canister drivesthe piercing plunger back out into the slot 41 and gas floods theremainder of the release system via the port 50.

The interlock mechanism of the device 27 operates in the followingfashion: the pilot pulls the bail, 23 or 24, for ejecting from theaircraft. rotating the shaft 38 to pull the retainer clip 34 out of thedevice 27, whereupon the spring 60 compressed between the annularshoulder 59 of the gas canister pack and the annular shoulder 61 of thehousing 42 ejects the gas canister pack out the open end of the housing42. With the high pressure gas canister removed from the device 27.there is no possibility of pressurizing the remainder of thegas-actuated release system.

Description of the Gas-Energized Releasable Latch Securing the SurvivalKit Referring now to FIGS. 50, b & c, the gas-energized releasable latchsecuring the survival pack 14 to the parachute harness worn by a pilotcomprises a female member 66 attached to the survival package 14 and amale member 67 adapted to be secured to a strap connected to theparachute harness. ln more detail, in the exploded view shown in FIG.5a, the female member 66 comprises a solid housing 68 having acylindrical horizontal passageway 69. One end of the passageway isthreaded for receiving a conventional gas line connector 71. The otherend of the passageway has an annular slot for receiving a conventionalcircular retaining clip 72. A locking plunger 73 disposed in thehorizontal passageway 69 includes a solid cylindrical locking section 74connected to a piston section 76 by a bar 77. A spring 78 is compressedbetween the circular retaining clip 72 and the cylindrical lockingsection 74 of the locking plunger 73 such that the piston section 76 ofthe plunger 73 is pushed against the gas line connector 7] (see FIG.5b). The housing 68 includes a rectangular passageway 79 perpendicularlyintersecting the cylindrical passageway 69. The rectangular passagewayis adapted to receive the male member of the latch.

In particular. the male member of the latch 67 comprises a conventionalrectangular bail 8l for securing a webbing strap having a rectangularlatching member 82 extending perpendicularly outward therefrom. Thelatching member 82 has a cylindrical recess 83 proximate its extendingend which has the same radial dimension as the cylindrical passageway 69of the female member 66 such that when the latching member 82 isinserted into the rectangular passageway 79 of the female member 66, thehorizontal cylindrical passageway 69 is unimpeded.

As shown in FIGS. 5b & 50, when the described latching mechanism islocked. the latch member 82 of the male member 67 is inserted into therectangular passageway 79 of the female member 66. The locking plunger73 is inserted into the cylindrical passageway 69 such that its lockingsection is disposed at the intersection of the latching member 82 andthe passageway 69, thus locking the male and female members together.The piston section 76 of the locking plunger 73 includes an annular slotfor receiving an O-ring 75. The O-ring makes a hermetic seal between thecylindrical walls of the passageway 69 and the piston section 76.

When the latch is energized with gas, the pressure drives the lockingplunger 73 against the spring 78 moving the locking section 74 of theplunger 73 out of engagement with the latching member 82 of the malemember 67. The small diameter bar 77 between the locking section andpiston section of the plunger 73 is designed such that it will notengage the latching member 82. Thus, the male member will pull free ofthe female member.

Detailed Description of the Gas-Energized Releasable Latch Securing theParachute Pack Referring now to FIGS. 6a throughf, the latch 16 securingthe riser strap 17 to the parachute pack 12 to the pilot's parachutepack comprises a solid rectangular member 84 having a cylindricalpassageway 86 along its central longitudinal axis. The rectangularmember 84 includes 2 integral extending flanges having coaxialcylindrical holes 88 therethrough. A webbing pin 89 is received by thecylindrical holes 88 for securing the riser strap 17.

One end of the cylindrical passageway 86 is adapted to receive aconventional gas line connector elbow 91. The other end of thepassageway 86 has an annular slot 92 for receiving a conventionalcircular retaining clip 93. A locking plunger 94 is disposed in thepassageway 86. The plunger 94 includes a cylindrical locking section 96fitting within the passageway 86 connected to a piston section 97 by asmall diameter bar 98. The piston section 97 of the plunger 94 has anannular slot 99 for receiving an O-ring 101 seal for making a hermeticseal between the piston and the walls of the passageway 86. A spring 102is disposed between the retaining clip 93 and the end of the lockingsection 96 of the plunger 94.

The rectangular bar 84 of the latch also has a rectangular passageway103 which perpendicularly intersects the cylindrical passageway 86. Therectangular passageway I03 is adapted to receive a rectangular latchingsection 104.

In more detail, the latching section 104 comprises the male prong 106 ofa conventional parachute release device having a rectangular shank 107extending from their base. The rectangular shank 107 has a recess I08perpendicular to its axis.

When the described latch is locked, the rectangular shank 107 of thelatching section 104 is inserted into the rectangular passageway 103through the rectangular structural member 84 such that the recess 108coincides with the passageway 86. The locking plunger 94 is insertedinto the passageway 86 such that the cylindrical locking section 96 ofthe plunger 94 engages the recess 108 of the latching section 104, thuspreventing the latching section from being pulled free of therectangular bar 84. The spring 102 holds the locking plunger 94 in thelocking position as described above.

When the described latch is energized with pressurized gas, the lockingplunger 94 is driven against the spring 102 bringing the locking section96 up to the plunger out of engagement with the recess 108 at the end ofthe shank 107 of the latching section 104, thus allowing the latchingsection to be pulled free of the rectangular bar 84.

Description of Tension Release Gas Line Connectors Referring now toFIGS. 7a, b & c. the tension release gas line connector 109 comprises 3coaxial cylindrical elements fitted together. The elements starting fromthe outside are: a cylindrical sleeve 11], a receiving cylinder 112 anda probe element 113. The sleeve cylinder 111 has an inwardly extendingannular shoulder 114 at one end and an annular slot [16 cut into theinside surface wall at the other end for receiving a conventionalcircular retaining clip 117. An annular groove 118 is cut into theinside wall of the sleeve 11 proximate the annular slot 116. Thecylindrical receiving element 112 is coaxially fitted within the sleeve111. and is connected by a tubular element 119 to the flexible hose fromthe releasable latches securing the survival kit and parachute. Theconfiguration of the inside wall of the cylindrical receiving element isdescribed with respect to FIG. 7a from left to right. First, there is anannular pocket 120 of relatively longitudinal width, then an annularslot 121 for receiving an O-ring seal 122, and an annular groove 123.

The probe element 113 is inserted coaxially into the cylindricalreceiving element 112. The O-ring 122 makes a hermetic seal between theinside wall of the receiving element 112 and the outside surface of theprobe element 113. One end of the probe 113 is adapted to be connectedto a flexible gas line from the ejection seat system 11. The free end ofthe probe element 113 has a plurality of holes 124 which communicatefrom the inside volume of the probe element to the annular pocket 120when inserted into the receiving cylinder 112. Two annular slots 126 arecut into the inside wall of the probe element 113 on either side of theholes 124 for receiving O-ring seals 127. The probe element 113 has asecond row of holes 128 which come into registry with the annular recess123 of the cylindrical receiving element 112 when the probe is insertedinto the coupling. Steel locking balls 129 are disposed in the holes128. The probe further includes an annular groove 131 around the outsidesurface of the probe between the holes 128 and the connected end of theprobe 113.

As shown in FIG. 7a, a retaining sleeve 132 having an annular shoulder133 with an outer diameter equal to the outer diameter of thecylindrical receiving element 112 and an inner diameter slightly greaterthan the outer diameter of the probe element 112 abuts against the endof the cylindrical receiving element 112 and is held in that abuttingrelationship by a spring 134 compressed between the circular retainingclip "7 and the extending annular shoulder 133 of the sleeve. A row ofholes 136 are cut perpendicularly through the shoulder 133 of theretaining sleeve 132 for receiving steel release balls 137. The diameterof the release balls 137 is greater than the thickness of thecylindrical receiving element 112. Accordingly, when the probe element113 is inserted into the cylindrical receiving unit 112 the releaseballs 137 are received in the annular recess 131 around the outsidesurface of the probe.

A locking plunger 138 having a small diameter section 139 and a largediameter section 141 is disposed within the probe element 113 such thatthe locking balls 129 disposed in the holes 128 rest on the smalldiameter section 139 of the plunger. An annular pocket 142 is cut aroundthe outside surface of the plunger 138. A central passageway 143 isdrilled along the longitudinal axis of the plunger and a port 144 isdrilled from the annular pocket 142 to the passageway such that a gascan flow through the plunger into the pocket. The plunger 138 also hasan annular slot 146 cut into its outside surface for receiving an O-ringseal 147. The O-ring makes a hermetic seal between the plunger and theinner surface of the probe element 113. The upstream end of the lockingplunger comprises a plurality of extending fingers 148 having a raisedsection 149 at their ends. The raised sections 149 at the ends of thefingers 148 are received in an annular groove 151 cut into the insidewall of the probe element 113. The annular grooves 151 have an abruptshoulder on the upstream side and an inclined shoulder on the downstreamside of the groove. The inner wall of the probe element also includes asecond annular groove 152 downstream fromthe groove 151.

The end of the tubular element 119 connected to the cylindricalreceiving element 112 includes a solid stop 153 having a cylindricalrecess for receiving the small diameter section 139 of the lockingplunger 138. A plurality of ports 155 are cut through the wall of thetubular element so that gas can communicate from the annular pocket 120into the passageway of the tubular element 119.

The described tension release gas line connector has 3 functional modes:(I) the unlatched or disconnect mode shown in FIG. 7b; (2) the tensionrelease or breakaway mode shown in FIG. 7c; and, (3) gas communicatingmode shown in FIG. 7d. The functional modes of the described connectorare described in the above order.

To unlatch or disconnect the tension release gas line connector 109, theannular sleeve is moved in the direction of the arrow compressing thespring 133 until the annular recess comes into registry with the releaseballs 137 contained in the holes 136 between the abutting ends of thecylindrical receiving element 112 and the retaining sleeve 132,whereupon the probe element is pulled in the direction of the arrow 135,causing the release balls to push into the recess 118. It should benoted that in the unlatching or disconnect mode, that the cylindricalreceiving element 112 and the retaining sleeveremain stationary withrespect to each other. To recouple the connector, the procedure issimply repeated bringing the annular recess 115 into registry with therelease balls 137 and then inserting the probe element 113.

- The tension release or breakaway functional mode of the describedconnector can be described as follows:

the sleeve Ill and the cylindrical receiving element move together inthe direction of the arrow H0. Simultaneously, the probe element movesin the direction of the arrow [35. The release halls 137 restrained bythe inside surface wall of the sleeve ll 1 and the annular recess 131 onthe outside surface of the probe [13 move with the retaining sleeve 132until the balls 137 come into registry with the annular recess H5 andthe sleeve whereupon the balls move outward and the probe pulls free ofthe connector.

In the gas communicating functional mode (FIG. 71!) of the connector,gas pressure drives the locking plunger 138 downstream in the directionof the arrow 110 such that the large diameter section of the plunger 14]drives the locking balls [29, disposed in the holes l28, upward into theannular recess 123 on the inside wall of the cylindrical receivingelement 112, thus locking the probe and receiving element together. Thestop 153 at the end of the tubular element 8 stops the plunger 134 suchthat its annular pocket 142 is between the two O-ring seals 127. Gasflows through the connector via the central passageway 143 through theplunger 138 out the port I44 into the annular pocket I20 through theports 155 into the central passage of the tubular element connected tothe flexible tubing going to the releasable latches. The annular groovel5l prevents the locking plunger [38 from sliding upstream in theconnector prior to pressurization. Upon pressurization, the raisedsections 149 of the locking fingers I48 are received in the annulargroove 152 to lock the plunger in a gas communicating position.

I claim:

1. In an aircraft equipped with an ejection seat system having anemergency ground egress release mechanism and an ejection escapemechanism, both being adapted to be activated by manual maneuvers of apilot:

an emergency pilot release system comprising in combination therewith:

a. a plurality of normally closed latching means for connecting a packedparachute canopy and a survival kit to a parachute harness worn by apilot, said packed parachute canopy and survival kit being releasablysecured to said ejection seat system;

b. energizing means mounted on said ejection seat system operativelycoupled to said emergency ground egress release mechanism for releasingand opening said latching means, said emergency ground egress releasemechanism being adapted to activate said energizing means;

c. fail-safe means operatively coupled to said ejection escape mechanismfor disabling said energizing means, the escape mechanism being adaptedto activate said fail-safe means;

d. a plurality of connector means, each connecting one of said latchingmeans to said energizing means. said connector means each havingconnective elements adapted to separate responsive to a tensile stress,whereby said pilot together with said parachute and survival kitconnected to his parachute harness will separate from said ejection seatsystem subsequent to an ejection escape from the aircraft; and

e. means for positively locking said connective elements of saidconnector means together upon activation of said energizing means,whereby said latching means are positively connected to said energizingmeans upon activation of said emergency ground egress release mechanism.

2. The emergency pilot release system of claim 1 wherein said energizingmeans comprises in combination:

a. a canister containing a highly compressed gas having a generallycylindrical neck section and a piercable membrane disposed across thatneck section;

b. a housing means mounted on said ejection seat system for holding saidcanister having means for piercing said membrane to release saidcompressed gas operatively connected to said emergency ground egressrelease mechanism; and

c. high pressure gas conduits connected between said housing means andthe plurality of connector means for receiving said compressed gas whenreleased from said canister and directing it to said latching means,said latching means being adapted to release and open uponpressurization by said compressed gas.

3. The emergency pilot release system of claim 2 further defined in thatsaid means for piercing said membrane comprises in combination:

a. a guide member integral with said housing having a slot orientedperpendicularly with respect to said neck section of said canister andhaving a passageway between said slot and said neck section of saidcanister, said passageway being axially aligned with said neck sectionof said canister;

b. a bar member received in said slot of said guide member having afirst and a second recess on a side contiguous to said passagewaybetween said slot and said neck section of said canister, said recessesbeing separated by a shoulder oriented perpendicularly with respect tosaid axis of said bar and having inclined sides, said bar member beingdisposed in said slot with said first recess in registry with saidpassageway;

c. mechanical meanas connected between said bar member and saidemergency ground egress release mechanism for moving said barlongitudinally in said slot bringing said second recess of said bar intoregistry with said passageway when said emergency ground egress releasemechanism is activated by said pilot; and

d. a piercing member disposed in said passageway of said guide memberhaving a rounded head extending into said slot received within saidfirst recess of said bar member and a piercing end disposed proximate tosaid membrane disposed across the neck section of said canister, wherebysaid piercing member is driven into said neck section of said canisterto pierce said memberane by the shoulder between said recesses as thesecond recess of the bar member is moved into registry with thepassageway whereupon pressure of the compressed gas forces the piercingmember out of the neck section of said canister, the rounded head ofsaid piercing member being received in said second recess in said barmember.

4. The pilot release system of claim 3 further defined in that a seal isdisposed around said piercing member for making a hermetic seal betweeinsaid piercing member and the wall of said passageway, and in that saidhousing has a port communicating with said passageway between the necksection of said canister and said hermetic seal, said high pressure gasconduits being connected to said port.

5. The emergency pilot release system of claim 4 further defined in thatsaid housing means for holding said canister comprises in combination:

a. a receiving member having a generally cylindrical cup-likeconfiguration. said guide member being integral with the closed end ofsaid receiving member and said passageway of said guide member beingaxially aligned with the axis of the receiving member;

b. a canister pack having a general cylindrical cuplike configurationshaving a hole through its closed end with means for hermeticallyengaging the neck section of said canister, said canister having agenerally cylindrical configuration and being coaxially disposed withinthe canister pack, which in turn is coaxially nested within saidreceiving member with said hole in registry with said passageway to saidslot of said guide member; and

c a seal disposed around said canister pack for making a hermetic sealbetween the walls of said canister pack and the walls .of said receivingmember.

6. The pilot release system of claim 5 further defined in that saidfail-safe means for disabling said energizing means comprises incombination:

a. an annular shoulder around the inside wall of said cylindricalcup-like receiving member;

b. an annular shoulder integral with the open end of said cylindricalcup-like canister pack having a greater diametric dimension than saidcanister pack;

c. means disposed between said annular shoulders of said receivingmember and said canister pack for ejecting said canister pack out theopen end of said receiving member;

d. releasable retaining means for securing said canister pack coaxiallywithin said receiving member; and

e. means operatively connected to said ejection escape mechanism of saidejection seat for releasing said releasable retaining means when saidejection escape mechanism is activated by said pilot whereby saidcanister pack is ejected out the open end of said receiving member thuspositively decoupling the canister containing said highly compressed gasfrom said emergency pilot release systern.

7. The pilot release system of claim 6 further defined in that saidmeans disposed between said annular shoulders of said receiving memberand said canister pack for ejecting said canister pack out the open endof said receiving members comprises a helical spring disposed around theoutside wall of said canister pack compressed between said annularshoulders.

8. The pilot release system of claim 7 further defined in that thecanister has an annular ring coaxially disposed around a portion of thecanister which extends out the open end of said canister pack, saidreleasable retaining means seating on said ring.

9. The pilot release system of claim 8 further defined in that a. saidcylindrical cup-like receiving member has two diametrically opposedslots through its walls proximate its opened end;

b. said releasable retaining means comprises a clip having two extendingprongs, said prongs having cylindrical seating sections at theirrespective ends adapted to grip said ring around said canister with aslight compressive force, said clip being clipped to said canisterthrough said diametrically opposed slots defined through the walls ofthe receiving member. said spring being compressed between therespective annular shoulder of the receiving member and the canisterpack forcing the annular shoulder at the open end of the canister packinto engagement with the extending prongs of said clip which are in turnrigidly held by said slots whereby said clip secures said canister packwithin said receiving member; and

c. said means for releasing said releasable retaining means is connectedto said clip and pulls said clip free of said receiving member whereuponsaid spring ejects said canister pack out the opened end of saidreceiving member.

10. The release system of claim 9 further defined in that said meansoperatively connected to said ejection escape mechanism for pulling saidclip free of said receiving member comprises a cable connected betweensaid clip and said ejection escape mechanism H. The emergency pilotrelease system of claim 2 wherein each of said normally closed latchingmeans comprise in combination:

a. a female member having a receiving passageway and a lockingpassageway perpendicularly intersecting said receiving passageway, saidlocking passageway having means for engaging a high pressure gas conduitat a first end and an inwardly extending annular shoulder at a secondend;

b. a male member having an extending shank, said shank having a recessoriented perpendicularly with respect to its longitudinal axis proximateits end, said shank being received in said receiving passageway of samefemale member with said recess in registry with said locking passagewayperpendicularly intersecting said receiving passageway;

c. a latch member disposed in said locking passageway of said femalemember having a latching section, a piston section and a small diameterbar connecting said latching section to said piston section; a springdisposed between said inwardly extending annular shoulder at the secondend of said locking passageway and the latching section of the latchmember for holding said latch section in registry with the intersectionof said locking and receiving passageways to thereby secure said shankof said male member in said receiving passageway of said female member,whereby a compressed gas introduced into said locking passageway via ahigh pressure gas conduit connected to the first end of the lockingpassageway longitudinally in said locking passageway against said springmoving the latch section of the latch member out of registry with theintersection of said receiving and locking passageways thereby releasingthe shank of the male member in the receiving passageway of the femalemember whereupon the compressed gas forces said shank out of saidreceiving passageway.

12. The pilot release system of claim 11 further defined in that a. thefemale member of at least two of said normally closed releasablelatching means are adapted for connection to riser straps from saidpacked parachute canopy; and

b. the male members for said female members adapted for connection tothe parachute riser straps include prongs axially extending from saidshank adapted for engagment in a manual release mechanism connected tothe parachute harness worn by the pilot.

13. The pilot release system of claim 11 further defined in that a. atleast two of said female members of said normally closed releasablelatching means are adapted to be mounted on said survival kit onopposite sides thereof; and

b. said male members for said female members secured to said survivalkit have a rectangular bail structure securing a strap, said straphaving means for connection to said parachute harness worn by the pilot.

14. The pilot release system of claim 2 further defined in that each ofsaid connector means further includes:

a. a first flexible high pressure gas conduit having a first endconnected to said conduit from said energizing means and a second endconnected to one of said connective elements of said connector means;

b, a second flexible high pressure gas conduit having a first endconnected to said normally closed latching means and a second endconnected to another of said connective elements of said connector meansin axial alignment with said second end of said first flexible highpressure conduit, whereby, when said pilot, parachute canopy andsurvival kit separate from the ejection seat system subsequent to anejection escape from the aircraft a tensile stress is applied along abreakway axis of the connector means, whereupon said connector meanspulls apart.

15. The pilot release system of claim 14 further defined in that saidconnective elements of said connector means comprise, in combination,

a. a cylindrical sleeve having annular shoulders extending inwardly at afirst end and a second end and having an annular groove cut into itsinside wall proximate to said second end,

b. a hollow receiving cylinder coaxially disposed within saidcylindrical sleeve having means for connection to said second end ofsaid second flexible high pressure gas conduit at a first end and anannular locking groove cut into its inside wall proximate a second end.said gas conduit adapted to extend coaxially out of said first end ofsaid cylindrical sleeve,

c. a hollow, cylindrical retaining element disposed coaxially withinsaid sleeve abutting against the second end of said receiving cylinder,said retaining sleeve having an annular shoulder section with an outerdiametric dimension approximately equal to the inner diametric dimensionof said cylindrical sleeve and having a sleeve section with a diametricdimension less than that of the cylindrical sleeve, said annularshoulder section of said retaining element having a circular row ofholes each containing a ball, said balls having a greater diametricdimension than the thickness dimension ofsaid annular shoulder sectionof said retaining element,

d. a spring disposed around said sleeve section of the retaining elementadapted to be compressed between said shoulder section of the retainingelement and the inwardly extending annular shoulder at said second endof said cylindrical sleeve,

e. a probe member having a central passageway received coaxially withinthe receiving cylinder and the retaining element having a first end anda second end extending axially out the second end of the cylindricalsleeve having means for connection to said second end of said firstflexible high pressure gas conduit and having a circular row of holeseach containing a ball, said balls having a greater diametric dimensionthan the thickness dimension of said probe member, said circular row ofholes containing said balls being in registry with said annular lockinggroove within the receiving cylinder, said probe member further havingan annular connecting groove in its outside wall located in registrywith the circular row of holes containing the balls in said shouldersection of said retaining element, whereby said balls within said holesof said retaining element rest on the inside wall of said cylindricalsleeve and extend into said annular connecting groove around said probemember mechanically coupling said probe member to said retaining elementsuch that the spring disposed between the annular shoulder section ofsaid retaining element and the inwardly extending shoulder of the secondend of the cylindrical sleeve resists tensile stresses tending toseparate the probe member and the receiving cylindrical until theannular groove cut into the inside wall of the cylindrical sleeve comesinto registry with the circular row of holes containing balls in theannular shoulder section of the retaining element whereupon said ballsmove outward into said annular groove thereby releasing the mechanicalcoupling between the probe member and the retaining element allowingsaid probe member to pull free of said coupling, and

further defined in that said means for positively locking saidconnective elements of said connecting means together comprises, incombination therewith, a locking plunger disposed in said centralpassageway of said probe member having a small diameter section disposedin registry with said circular row of holes containing balls in saidprobe member separated from a large diameter section with a diametricdimension approximately equal to the inner diametric dimension of saidpassageway by an inclined section, said plunger further having anannular pocket around the large diameter section, and a fluid passagewaypartially through its large diameter section, and a port between saidfluid passageway and said annular pocket, whereby a gas introduced intosaid probe member via a fluid conduit connected to the second end of theprobe member drives said plunger into a locking position in said centralpassageway of said probe member, with the large diameter section of theplunger in registry with the circular row of holes through the probemember, the balls contained therein being forced outward into theannular locking groove of the receiving cylinder to thereby positivelymechanically couple the probe member to the receiving cylinder, said gasflowing through the connector via the fluid passageway through theplunger,

out the port into the annular pocket and into the receiving cylinder andout a high pressure conduit connected to the receiving cylinder.

16. The pilot release system of claim 15 further defined in that a saidprobe member includes a circular row of ports proximate its first end;

b. said receiving cylinder includes a stop for arresting translation ofsaid locking plunger within the central passageway of said probe memberwhen the annular pocket around said locking plunger moves into registrywith said ports;

c. said receiving cylinder has a relieved annular section cut into itsinside wall proximate its first end, whereby an annular plenum isdefined around the first end of said probe member in registry with itscircular row ports; and

d. said receiving cylinder further has a plurality of portscommunicating between the annular plennum and a fluid conduit connectedto the first end of the receiving cylinder 17. The pilot release systemof claim 16 further defined in that v a. the locking plunger and thecentral passageway of the probe member each have a generally cylindricalconfiguration;

hi the locking plunger further includes a plurality of fingers extendingfrom the large diameter section parallel the axis of the plunger. eachof said fingers having a raised section at their distal end; and

c. the central passageway of said probe member has a first annularkeeper groove proximate its second end receiving said raised sections onthe end of said fingers for keeping the small diameter section of saidlocking plunger in registry with said circular row of holes through saidprobe member. and has a second annular keeper groove for receiving saidraised sections on the end of said fingers when the plunger is driven tothe locking position within the central passageway and for keeping saidplunger in said locking position.

18. The pilot release system of claim 17 further defincd in that a. afirst annular seal is disposed within said receiving cylinder for makinga hermetic seal between the probe member and the inside wall of thereceiving cylinder;

b. a second annular seal is disposed within said central passageway ofthe probe member between the first end thereof and the circular row ofports therethrough; and

c. a third annular seal is disposed within said central passageway ofthe probe member between the circular row of ports and the circular rowof holes containing balls, whereby said second and third seals fromhermetic seals between the walls of the central passageway and the largediameter section of the locking plunger when said plunger is trans latedinto the locking position. l i

1. In an aircraft equipped with an ejection seat system having anemergency ground egress release mechanism and an ejection escapemechanism, both being adapted to be activated by manual maneuvers of apilot: an emergency pilot release system comprising in combinationtherewith: a. a plurality of normally closed latching means forconnecting a packed parachute canopy and a survival kit to a parachuteharness worn by a pilot, said packed parachute canopy and survival kitbeing releasably secured to said ejection seat system; b. energizingmeans mounted on said ejection seat system operatively coupled to saidemergency ground egress release mechanism for releasing and opening saidlatching means, said emergency ground egress release mechanism beingadapted to activate said energizing means; c. fail-safe meansoperatively coupled to said ejection escape mechanism for disabling saidenergizing means, the escape mechanism being adapted to activate saidfail-safe means; d. a plurality of connector means, each connecting oneof said latching means to said energizing means, said connector meanseach having connective elements adapted to separate responsive to atensile stress, whereby said pilot together with said parachute andsurvival kit connected to his parachute harness will separate from saidejection seat system subsequent to an ejection escape from the aircraft;and e. means for positively locking said connective elements of saidconnector means together upon activation of said energizing means,whereby said latching means are positively connected to said energizingmeans upon actIvation of said emergency ground egress release mechanism.2. The emergency pilot release system of claim 1 wherein said energizingmeans comprises in combination: a. a canister containing a highlycompressed gas having a generally cylindrical neck section and apiercable membrane disposed across that neck section; b. a housing meansmounted on said ejection seat system for holding said canister havingmeans for piercing said membrane to release said compressed gasoperatively connected to said emergency ground egress release mechanism;and c. high pressure gas conduits connected between said housing meansand the plurality of connector means for receiving said compressed gaswhen released from said canister and directing it to said latchingmeans, said latching means being adapted to release and open uponpressurization by said compressed gas.
 3. The emergency pilot releasesystem of claim 2 further defined in that said means for piercing saidmembrane comprises in combination: a. a guide member integral with saidhousing having a slot oriented perpendicularly with respect to said necksection of said canister and having a passageway between said slot andsaid neck section of said canister, said passageway being axiallyaligned with said neck section of said canister; b. a bar memberreceived in said slot of said guide member having a first and a secondrecess on a side contiguous to said passageway between said slot andsaid neck section of said canister, said recesses being separated by ashoulder oriented perpendicularly with respect to said axis of said bar,and having inclined sides, said bar member being disposed in said slotwith said first recess in registry with said passageway; c. mechanicalmeanas connected between said bar member and said emergency groundegress release mechanism for moving said bar longitudinally in said slotbringing said second recess of said bar into registry with saidpassageway when said emergency ground egress release mechanism isactivated by said pilot; and d. a piercing member disposed in saidpassageway of said guide member having a rounded head extending intosaid slot received within said first recess of said bar member and apiercing end disposed proximate to said membrane disposed across theneck section of said canister, whereby said piercing member is driveninto said neck section of said canister to pierce said memberane by theshoulder between said recesses as the second recess of the bar member ismoved into registry with the passageway whereupon pressure of thecompressed gas forces the piercing member out of the neck section ofsaid canister, the rounded head of said piercing member being receivedin said second recess in said bar member.
 4. The pilot release system ofclaim 3 further defined in that a seal is disposed around said piercingmember for making a hermetic seal betweein said piercing member and thewall of said passageway, and in that said housing has a portcommunicating with said passageway between the neck section of saidcanister and said hermetic seal, said high pressure gas conduits beingconnected to said port.
 5. The emergency pilot release system of claim 4further defined in that said housing means for holding said canistercomprises in combination: a. a receiving member having a generallycylindrical cup-like configuration, said guide member being integralwith the closed end of said receiving member and said passageway of saidguide member being axially aligned with the axis of the receivingmember; b. a canister pack having a general cylindrical cup-likeconfigurations having a hole through its closed end with means forhermetically engaging the neck section of said canister, said canisterhaving a generally cylindrical configuration and being coaxiallydisposed within the canister pack, which in turn is coaxially nestedwithin said receiving member with said hole in registry with saidpassageway to said slot of said guide member; and c. A seal disposedaround said canister pack for making a hermetic seal between the wallsof said canister pack and the walls of said receiving member.
 6. Thepilot release system of claim 5 further defined in that said fail-safemeans for disabling said energizing means comprises in combination: a.an annular shoulder around the inside wall of said cylindrical cup-likereceiving member; b. an annular shoulder integral with the open end ofsaid cylindrical cup-like canister pack having a greater diametricdimension than said canister pack; c. means disposed between saidannular shoulders of said receiving member and said canister pack forejecting said canister pack out the open end of said receiving member;d. releasable retaining means for securing said canister pack coaxiallywithin said receiving member; and e. means operatively connected to saidejection escape mechanism of said ejection seat for releasing saidreleasable retaining means when said ejection escape mechanism isactivated by said pilot whereby said canister pack is ejected out theopen end of said receiving member thus positively decoupling thecanister containing said highly compressed gas from said emergency pilotrelease system.
 7. The pilot release system of claim 6 further definedin that said means disposed between said annular shoulders of saidreceiving member and said canister pack for ejecting said canister packout the open end of said receiving members comprises a helical springdisposed around the outside wall of said canister pack compressedbetween said annular shoulders.
 8. The pilot release system of claim 7further defined in that the canister has an annular ring coaxiallydisposed around a portion of the canister which extends out the open endof said canister pack, said releasable retaining means seating on saidring.
 9. The pilot release system of claim 8 further defined in that a.said cylindrical cup-like receiving member has two diametrically opposedslots through its walls proximate its opened end; b. said releasableretaining means comprises a clip having two extending prongs, saidprongs having cylindrical seating sections at their respective endsadapted to grip said ring around said canister with a slight compressiveforce, said clip being clipped to said canister through saiddiametrically opposed slots defined through the walls of the receivingmember, said spring being compressed between the respective annularshoulder of the receiving member and the canister pack forcing theannular shoulder at the open end of the canister pack into engagementwith the extending prongs of said clip which are in turn rigidly held bysaid slots whereby said clip secures said canister pack within saidreceiving member; and c. said means for releasing said releasableretaining means is connected to said clip and pulls said clip free ofsaid receiving member whereupon said spring ejects said canister packout the opened end of said receiving member.
 10. The release system ofclaim 9 further defined in that said means operatively connected to saidejection escape mechanism for pulling said clip free of said receivingmember comprises a cable connected between said clip and said ejectionescape mechanism.
 11. The emergency pilot release system of claim 2wherein each of said normally closed latching means comprise incombination: a. a female member having a receiving passageway and alocking passageway perpendicularly intersecting said receivingpassageway, said locking passageway having means for engaging a highpressure gas conduit at a first end and an inwardly extending annularshoulder at a second end; b. a male member having an extending shank,said shank having a recess oriented perpendicularly with respect to itslongitudinal axis proximate its end, said shank being received in saidreceiving passageway of same female member with said recess in registrywith said locking passageway perpendicularly intersecting said receivingPassageway; c. a latch member disposed in said locking passageway ofsaid female member having a latching section, a piston section and asmall diameter bar connecting said latching section to said pistonsection; d. a spring disposed between said inwardly extending annularshoulder at the second end of said locking passageway and the latchingsection of the latch member for holding said latch section in registrywith the intersection of said locking and receiving passageways tothereby secure said shank of said male member in said receivingpassageway of said female member, whereby a compressed gas introducedinto said locking passageway via a high pressure gas conduit connectedto the first end of the locking passageway longitudinally in saidlocking passageway against said spring moving the latch section of thelatch member out of registry with the intersection of said receiving andlocking passageways thereby releasing the shank of the male member inthe receiving passageway of the female member whereupon the compressedgas forces said shank out of said receiving passageway.
 12. The pilotrelease system of claim 11 further defined in that a. the female memberof at least two of said normally closed releasable latching means areadapted for connection to riser straps from said packed parachutecanopy; and b. the male members for said female members adapted forconnection to the parachute riser straps include prongs axiallyextending from said shank adapted for engagment in a manual releasemechanism connected to the parachute harness worn by the pilot.
 13. Thepilot release system of claim 11 further defined in that a. at least twoof said female members of said normally closed releasable latching meansare adapted to be mounted on said survival kit on opposite sidesthereof; and b. said male members for said female members secured tosaid survival kit have a rectangular bail structure securing a strap,said strap having means for connection to said parachute harness worn bythe pilot.
 14. The pilot release system of claim 2 further defined inthat each of said connector means further includes: a. a first flexiblehigh pressure gas conduit having a first end connected to said conduitfrom said energizing means and a second end connected to one of saidconnective elements of said connector means; b. a second flexible highpressure gas conduit having a first end connected to said normallyclosed latching means and a second end connected to another of saidconnective elements of said connector means in axial alignment with saidsecond end of said first flexible high pressure conduit, whereby, whensaid pilot, parachute canopy and survival kit separate from the ejectionseat system subsequent to an ejection escape from the aircraft a tensilestress is applied along a breakway axis of the connector means,whereupon said connector means pulls apart.
 15. The pilot release systemof claim 14 further defined in that said connective elements of saidconnector means comprise, in combination, a. a cylindrical sleeve havingannular shoulders extending inwardly at a first end and a second end andhaving an annular groove cut into its inside wall proximate to saidsecond end, b. a hollow receiving cylinder coaxially disposed withinsaid cylindrical sleeve having means for connection to said second endof said second flexible high pressure gas conduit at a first end and anannular locking groove cut into its inside wall proximate a second end,said gas conduit adapted to extend coaxially out of said first end ofsaid cylindrical sleeve, c. a hollow, cylindrical retaining elementdisposed coaxially within said sleeve abutting against the second end ofsaid receiving cylinder, said retaining sleeve having an annularshoulder section with an outer diametric dimension approximately equalto the inner diametric dimension of said cylindrical sleeve and having asleeve section with a diametric dimension less than that of thecylIndrical sleeve, said annular shoulder section of said retainingelement having a circular row of holes each containing a ball, saidballs having a greater diametric dimension than the thickness dimensionof said annular shoulder section of said retaining element, d. a springdisposed around said sleeve section of the retaining element adapted tobe compressed between said shoulder section of the retaining element andthe inwardly extending annular shoulder at said second end of saidcylindrical sleeve, e. a probe member having a central passagewayreceived coaxially within the receiving cylinder and the retainingelement having a first end and a second end extending axially out thesecond end of the cylindrical sleeve having means for connection to saidsecond end of said first flexible high pressure gas conduit and having acircular row of holes each containing a ball, said balls having agreater diametric dimension than the thickness dimension of said probemember, said circular row of holes containing said balls being inregistry with said annular locking groove within the receiving cylinder,said probe member further having an annular connecting groove in itsoutside wall located in registry with the circular row of holescontaining the balls in said shoulder section of said retaining element,whereby said balls within said holes of said retaining element rest onthe inside wall of said cylindrical sleeve and extend into said annularconnecting groove around said probe member mechanically coupling saidprobe member to said retaining element such that the spring disposedbetween the annular shoulder section of said retaining element and theinwardly extending shoulder of the second end of the cylindrical sleeveresists tensile stresses tending to separate the probe member and thereceiving cylindrical until the annular groove cut into the inside wallof the cylindrical sleeve comes into registry with the circular row ofholes containing balls in the annular shoulder section of the retainingelement whereupon said balls move outward into said annular groovethereby releasing the mechanical coupling between the probe member andthe retaining element allowing said probe member to pull free of saidcoupling, and further defined in that said means for positively lockingsaid connective elements of said connecting means together comprises, incombination therewith, a locking plunger disposed in said centralpassageway of said probe member having a small diameter section disposedin registry with said circular row of holes containing balls in saidprobe member separated from a large diameter section with a diametricdimension approximately equal to the inner diametric dimension of saidpassageway by an inclined section, said plunger further having anannular pocket around the large diameter section, and a fluid passagewaypartially through its large diameter section, and a port between saidfluid passageway and said annular pocket, whereby a gas introduced intosaid probe member via a fluid conduit connected to the second end of theprobe member drives said plunger into a locking position in said centralpassageway of said probe member, with the large diameter section of theplunger in registry with the circular row of holes through the probemember, the balls contained therein being forced outward into theannular locking groove of the receiving cylinder to thereby positivelymechanically couple the probe member to the receiving cylinder, said gasflowing through the connector via the fluid passageway through theplunger, out the port into the annular pocket and into the receivingcylinder and out a high pressure conduit connected to the receivingcylinder.
 16. The pilot release system of claim 15 further defined inthat a. said probe member includes a circular row of ports proximate itsfirst end; b. said receiving cylinder includes a stop for arrestingtranslation of said locking plunger within the central passageway ofsaid probe member when the annular pocket around said locking plungermoves into registry with said ports; c. said receiving cylinder has arelieved annular section cut into its inside wall proximate its firstend, whereby an annular plenum is defined around the first end of saidprobe member in registry with its circular row ports; and d. saidreceiving cylinder further has a plurality of ports communicatingbetween the annular plennum and a fluid conduit connected to the firstend of the receiving cylinder.
 17. The pilot release system of claim 16further defined in that a. the locking plunger and the centralpassageway of the probe member each have a generally cylindricalconfiguration; b. the locking plunger further includes a plurality offingers extending from the large diameter section parallel the axis ofthe plunger, each of said fingers having a raised section at theirdistal end; and c. the central passageway of said probe member has afirst annular keeper groove proximate its second end receiving saidraised sections on the end of said fingers for keeping the smalldiameter section of said locking plunger in registry with said circularrow of holes through said probe member, and has a second annular keepergroove for receiving said raised sections on the end of said fingerswhen the plunger is driven to the locking position within the centralpassageway and for keeping said plunger in said locking position. 18.The pilot release system of claim 17 further defined in that a. a firstannular seal is disposed within said receiving cylinder for making ahermetic seal between the probe member and the inside wall of thereceiving cylinder; b. a second annular seal is disposed within saidcentral passageway of the probe member between the first end thereof andthe circular row of ports therethrough; and c. a third annular seal isdisposed within said central passageway of the probe member between thecircular row of ports and the circular row of holes containing balls,whereby said second and third seals from hermetic seals between thewalls of the central passageway and the large diameter section of thelocking plunger when said plunger is translated into the lockingposition.